Stabilizer for flying apparatus sustained by propellers



Dec, 16, 1924.

1,519,866 A. MARCHETTI STABILIZER FOR FLYING APPARATUS SUSTAINED BY PRORELLERS Filed June 29. 1921 2 Sheets-Sheet l Dec. 16, 1924 1,519,866

A. MARCHETTI STABILIZER FOR FLYING APPARATUS SUSTAINED BY PROPELLERS Filed June 29, 1921 2 Sheets-Sheet 2 Patented Dec. is, i924.

UNITED STATES ALESSANDRO MARCHETTI, F ROME, ITALY.

STABILIZEB FOR FLYINGy APPARATUS SUSTAINED BY PROPELLERS.

Application filed June 29, 1921.

.15 problem of the stability and the horizontal mobility of flying apparatus sustained by propellers.

By means of surfaces having a double .con-

veX section as set forth in the following specification the disposition and movements of which are absolutely characteristic, it is possible `to create aero-dynamic reactionsl substantially in the horizontal direction,

coplanar with the sustaining propellers of the flying apparatus.

The direction, magnitude, and sense of leach reaction are controllable at will.

Through these it is possible:

1. To counterbalance and annui a lateral n misbalance;

2. To produce the driving power and the lateral inclination necessary for motion in the horizontal sense.

Figure 1 is an elevation of the invention.

Figure 2 is a plan view of the same.

Figure 3 shows a conventional form of construction.

Figure 4 is an elevation partly in section showing the stabilizer as applied to the sustaining propeller.

Figure 5 is a top plan 4view of the propeller and stabilizer.

Figure 6 is a sectional view on the line 6 6 of Figure 4.

In the form of construction illustrated as an example in the accompanying drawings, the continuous relative movements in the two senses of the double vconvex surfaces is realized by means of a ring D provided with a circular groove G surrounding the sustaining nropeller shaft A. said groove serving as a guide for a small pin or stud 'fr'- integral with a connecting rod a connected to the double convex surface by a lever f L; said rod traveling about the said groove Serial No. 481,272.

G .which is adjustably mounted about the axis capable of being moved into positions eccentric thereto. It will be evident that a movement of the circular grooverelatively to the shaft A will cause variation in phase and. amplitude of the periodicaloperation during turning of the double convex surfaces, said variations being by suitable means kept within strictly defined and predetermined limits. A

Referring more particularly to the enclosed drawings :--v

One or more Vertical surfaces S mounted on one or more arms B, are rapidly bodily displaced in space due to the revolving movement of the shaft A, as shown by the arrow F.y

Their path is circular relatively to A. In addition each surface is adapted to be rotated on its own axis through small angles on their side of the tangential position by means of the pivot O, having a vertical axis parallel to A, this motion being controlled mechanically at will by the pilot, through any convenient apparatus such as shown in Figure 3. The vinclination of these surfaces is periodically controlled so that the inclination passes from a positive value, in the positions shown at 8, l and 2 (Fig. 2) through zero at 3, to an opposite position at 4, 5 and 6 and back again to zero at 7 in predetermined sectors so as to furnish the reaction created by the oblique aerodynamic incidence on the relative wind. Consequently, c orresponding to the inclination relative to the wind that the surfaces are given in such a rotation, aerodynamic thrust reactions are created on the surfaces, normal to the shaft A. In consequence of the surfaces having no incidence in some of the sectors thetotal resultant force from a lurality of such .surfaces is constituted: 1st) by a component tangential to the circle described by the said surfaces which component is counter-balanced by the driving force; (2nd) by a radial component lying in the plane of rotation of the system. This radial force is used to obtain the mechanical effects mentioned and may be regulated inmagnitude'and direction by the pilot as desired.`

In this vway the reactions give a ultilizable thrust' component R in one direction, such direction being chosen at will by the pilot and varied at will, during motionby means of various mechanical ,devices such as shown lll in Figure 3. This characteristically periodical and continuouslyk changing motion causes the surfiaces S to localize the reactions vso 'dueto their aerodynamic incidence in predetermined sectors of their path about the shaft A, in passing which sectors the said surfaces assume a particular and suitable Obliquity relative to the wind, such Obliquity being variable at will and under the control of the pilot.

' These circumstances have the novel effect that while the surfaces S are continually and doubly in motion'aboutthe shaft A and theirv own axis, the field of. the reactive `strains created by them is fixed and localized movement (slight swinging of the surfaces on their axes relatively to the path) may be suppressed, in vwhich oase the annular groove is at that time coaxial with the shaft of the sustaining propeller.

The mechanical arrangement actuating the controllable and periodic movement of the surfaces can be constructed in many ways and does not form a part of the present in- ,vention which only refers to the stabilizingl means for flying apparatus sustained by propellers.

Forfpurpose 'of illustrationone form of controlling; mechanism is shown in Figure 3 of the drawing whe-rein the grooved ring D is sho-wn supported in a member which is adjustable and terminates in a control handle I. It will be understood that by the manipulation of the control handle thering D hereinbefore set forth.

may be made to move eccentrically with respect to the shaft A and produces the results "For the purpose of illustration ll have shown in Figures 4, 5' and 6 one possible Vembodiment of the invention in which the arms B form the blades of a prepeller (helicopter). vThese blades are shown in Figure 16 as being hollow and containing the operating mechanism forv kthe convexy survfaced vanes S mounted on said blades adiacentjto their outer extremitiesl as hereinbefore set forth. The vanes S are mounted for partialrotationy about vertical axes on vshafts O, carried by the: vblades B in suitable bearings and positioned on `axes parallel to the axis of thedrive shaft A. Se-

cured to the shafts lO are the crankarms L, "Which, by means of' connecting rods a are connected to the grooveG in the movable control ring D.

' As hereinbefore stated the bladesY Biare 1 hollow, the interiorv chambers so formed extending longitudinally of the blades and `mounted on the machine through the under and outer Wall thereof adjacent to the hub of the propeller, as clearly shown in Figure 4, whereby to provide connection between the connecting arms a and the ring D. The ring D is adapted to be displaced laterally relative to theshaft A by means of a mechanism such as illustrated in Figure 3 whereby the eccentricity of the ring with respect to the shaft may be varied wit-hin predetermined limits to alter the relative phase and amplitude of the vanes lS during rotation.

The device as shown in lthe` drawings, is' only'given as a mere example and it is understood that in the'mechanicalshaping of the contrivance all suitable alterations answering `to the purpose for whichv the apparatus is meant, may introducedfwithoutexceeding the scope of the present invention. A Having now particularly described and ascertained the nature of my said invention,

and inwhat mannerjthe same is kto be `performed- I declare that what `IY claimVv is :--l

1. lA stabilizer for flying apparatus sustained by propellers comprising a plurality of vanes carried l by th'e propeller blades and adapted to `rotate' bodily` therewith, and

vmeans tofadjust the vanes individually and 4periodically about raxes parellel to the axis of the propeller shaft.v A

2. A stabilizer "for flying apparatus of the helicopter" type comprising a plurality of arms carried by the propeller shaft, al plurality of vanes carried by the arms, said arms and vanes adapted to rotate bodily with the shaft to sustain the apparatus in the air, and means to simultaneously turn the vanes individually and periodically about axes parallel to the axis of thel propeller shaft,v and to vary the phase and amplitude of the vanes vduring'saidvturning whereby to stabilize the apparatus.

3. The combination with a flying machine having a propeller shaft, of a stabilizer comprisingfa propeller carried by the shaft, a plurality of vanes carried by the propeller and movable with respect thereto and adapted to rotate bodily therewith, a' ring adjacent to the hub of the propeller, and means carried by the vanes and lying' partially within the propellervconnecting said vanes to said ring whereby to move the vanes with vrespectto the propellers duringk thefbodily `rotation of the propeller and vanes.

4. vThe comb'nation with a flying machine having a propeller shaft,`of" a stabilizer comprising` a plurality of hollow armscarried by theyshaft and adapted tofv rotate therewith, a vane carriedv by each arm, vmeans positioned partially withinthe arms to ad'-` just the vanes individually and periodically,

, and means surrounding the propeller shaft y 1,519,soe

varying the phase and amplitude of the vanes during the rotation of the propeller.

5. A stabilizer for flying machines sustained by propellers, comprising a plurality of varies, means to simultaneously rotate the same bodily with the propeller shaft, and adjusting said vanes individually and periodically about axes parallel to that of the shaft, and means to vary the phases and amplitude of the vanes during said rotation.

6. A stabilizer for flying machines sustained by propellers, comprising a plurality of radial arms carried by the propeller shaft, and Vanes having double convex surfaces -mounted on each arm and adapted to rotate bodily therewith, a ring provided with an annular groove carried by the machine and surrounding the shaft adjacent to said arm, means connecting the Vanes and the ring and lying Within the arms, and means to Vary the eccentricity of the ring With respect to the shaft whereb to periodically vary the phase and amplitude of the vanes during rotation of the arms.

In testimony whereof I have hereunto signed my name.

ALESSANDRO MARCHETTI. 

